Laminar flow past oscillating Naca 0012 airfoil
I have to validate a new Dual Time Stepping algorithm. Mach number should be less than 0.3 and flow is laminar (Re~1000 to 20000).
I will be grateful if anyone could email me any decent paper presenting CL,Cd,Cm variation with angle of attack for oscillating Naca 0012 airfoil.
Thanks in advance
You can use Garrick's formula to compare your results. The formula works well as long as you do not have any flow separation. The paper is available from NASA server or you can look for dissertation of Young through google. Both of them will furnish you the analytical expressions. For a more detailed comparison, you can look for experiments by Lai and Platzer.
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